EP0674748B1 - Agencement de charniere a volets pour tuyere convergente-divergente - Google Patents

Agencement de charniere a volets pour tuyere convergente-divergente Download PDF

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Publication number
EP0674748B1
EP0674748B1 EP93909456A EP93909456A EP0674748B1 EP 0674748 B1 EP0674748 B1 EP 0674748B1 EP 93909456 A EP93909456 A EP 93909456A EP 93909456 A EP93909456 A EP 93909456A EP 0674748 B1 EP0674748 B1 EP 0674748B1
Authority
EP
European Patent Office
Prior art keywords
flap
divergent
convergent
gas side
hinge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP93909456A
Other languages
German (de)
English (en)
Other versions
EP0674748A1 (fr
Inventor
William Kevin Barcza
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP0674748A1 publication Critical patent/EP0674748A1/fr
Application granted granted Critical
Publication of EP0674748B1 publication Critical patent/EP0674748B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1223—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F02K1/008—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector in any rearward direction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/80—Couplings or connections
    • F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent

Definitions

  • the invention relates to gas turbine engines and in particular to vectorable discharge nozzles therefor.
  • Gas turbine engines for aircraft achieve thrust by discharging hot gases through the exhaust nozzle.
  • Efficient operation for multi-mission application dictates the use of variable area convergent/divergent nozzles.
  • Variable convergent/divergent configuration is achieved in axisymmetric nozzles by the use of a plurality of circumferentially arranged flaps. overlapping seals are located between adjacent flaps.
  • the hinge arrangement must be provided between each convergent flap or seal and each divergent flap or seal. Variations may be made during operation, of the throat and terminal discharge openings.
  • Increased maneuverability of the aircraft can be accomplished by thrust vectoring.
  • the discharge of gas is vectored from the axial direction to achieve a thrust component which is up, down or sideways.
  • the vectoring may be accomplished by vectoring movement of the divergent flaps and seals only.
  • the convergent flaps and seals remain symmetrical.
  • the hinges between the convergent and divergent flap must be capable of rotation around both the radial axis and lateral axis of the hinge. The hinge must also maintain a seal at all times to prevent leakage of the hot gas stream and loss of thrust.
  • Cooling air is discharged along the surface of the convergent nozzle, passing through the throat to the divergent nozzle.
  • the hinge must neither significantly affect the geometry of the nozzle throat nor block the cooling flow from the convergent nozzle.
  • Patent document WO 92/03649 shows a vectoring convergent/divergent nozzle having a hinge connection member pivotably connected to the downstream end of the convergent flap, the upstream end of the divergent flap further being pivotably connected to the hinge connection member.
  • Flap seals are formed of overlapping leaf seats with one of each pair of leaf seals being secured to the convergent flap and one being secured to a corresponding convergent flap.
  • a flap hinge arrangement for an axisymmetric vectorable convergent/divergent nozzle comprising:
  • the first connection is formed of two spaced coaxial pins with a space therebetween.
  • the second pivotable connection comprises a pin located in said space.
  • Figure 1 is a general view of convergent/divergent nozzle 10 with convergent flaps 12 and divergent flaps 14. Interposed between the flaps are convergent seals 16 and divergent seals 18.
  • planar gas side surface 56 of divergent flap 14 is coplanar with the gas side surface 46 of the divergent hinge flap seal 22.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Lift Valve (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Hinges (AREA)
  • Gasket Seals (AREA)
  • Preliminary Treatment Of Fibers (AREA)

Abstract

Un joint de charnière à volet divergent (22) pour une tuyère de vectorisation de poussée (10) est relié pivotant au volet convergeent (12) et le volet divergent (14) est relié pivotant à ce joint de charnière à volet (22). Un prolongement (48) du joint de charnière recouvre hermétiquement un évidement (50) ménagé dans le volet divergent (14).

Claims (4)

  1. Arrangement de charnière pour une tuyère convergente/divergente vectorisable à symétrie axiale, comprenant:
    un volet convergent variable (12) possédant une surface de volet convergent plane côté gaz;
    un joint étanche de charnière divergente (22) possédant une surface de joint étanche de charnière plane côté gaz;
    un volet divergent variable (14) possédant une surface de volet divergent plane côté gaz (56) coplanaire avec ladite surface de joint étanche de charnière plane côté gaz;
    un premier raccord pivotant (40) dont l'axe d'articulation (42) est parallèle à la fois à ladite surface de volet convergent plane côté gaz et à ladite surface de joint étanche de charnière plane côté gaz;
    ledit premier raccord pivotant (40) reliant ledit joint étanche de charnière divergente (22) et ledit volet convergent (12);
    et un second raccord pivotant (60) dont l'axe (62) est perpendiculaire à ladite surface de joint étanche de charnière côté gaz et reliant ledit joint étanche de charnière (22) et ledit volet divergent (14);
       caractérisé par le fait que:
    l'axe (42) dudit premier raccord pivotant et l'axe (62) dudit second raccord pivotant se coupent en formant un angle droit;
    la surface côté gaz dudit volet divergent présente une zone évidée (50) en position adjacente audit second raccord pivotant;
    et ledit joint étanche de charnière comporte un prolongement (48) chevauchant de manière étanche ladite zone évidée.
  2. Arrangement de charnière selon la revendication 1, comprenant également:
       le fait que ledit prolongement possède un bord arqué (52) dont le centre de courbure passe par ledit second raccord pivotant (60).
  3. Arrangement de charnière selon la revendication 2, comprenant également:
       le fait que la limite de ladite zone évidée (50) épouse la forme dudit bord arqué (52).
  4. Arrangement de charnière selon l'une quelconque des revendications 1 à 3, comprenant également:
    le fait que ledit premier raccord pivotant comprend deux broches coaxiales espacées (64), entre lesquelles est ménagé un espace;
    et le fait que ledit second raccord pivotant comprend une broche (58) logée dans ledit espace.
EP93909456A 1992-07-16 1993-03-18 Agencement de charniere a volets pour tuyere convergente-divergente Expired - Lifetime EP0674748B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US914289 1992-07-16
US07/914,289 US5215256A (en) 1992-07-16 1992-07-16 Flap hinge arrangement for a convergent/divergent nozzle
PCT/US1993/002755 WO1994002731A1 (fr) 1992-07-16 1993-03-18 Agencement de charniere a volets pour tuyere convergente-divergente

Publications (2)

Publication Number Publication Date
EP0674748A1 EP0674748A1 (fr) 1995-10-04
EP0674748B1 true EP0674748B1 (fr) 1997-08-27

Family

ID=25434144

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93909456A Expired - Lifetime EP0674748B1 (fr) 1992-07-16 1993-03-18 Agencement de charniere a volets pour tuyere convergente-divergente

Country Status (7)

Country Link
US (1) US5215256A (fr)
EP (1) EP0674748B1 (fr)
JP (1) JP3200686B2 (fr)
KR (1) KR100263797B1 (fr)
DE (1) DE69313461T2 (fr)
IL (1) IL105263A (fr)
WO (1) WO1994002731A1 (fr)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5245823A (en) * 1991-09-23 1993-09-21 United Technologies Corporation External flap vectoring mechanism
US5484105A (en) * 1994-07-13 1996-01-16 General Electric Company Cooling system for a divergent section of a nozzle
FR2723764B1 (fr) * 1994-08-18 1996-12-20 Snecma Etancheite entre volets suiveurs divergents et convergents d'une tuyere d'ejection de turboreacteur
US5667140A (en) * 1994-12-02 1997-09-16 United Technologies Corporation Engine exhaust nozzle seal
US5683034A (en) * 1995-05-22 1997-11-04 United Technologies Corporation Engine exhaust nozzle seal
US5680755A (en) * 1995-09-25 1997-10-28 General Electric Company Convertible ejector selectively cooled thrust vectoring exhaust nozzle
US5794850A (en) 1996-09-27 1998-08-18 United Technologies Corporation Enclosed pressure balanced sync ring nozzle
US5813611A (en) * 1996-09-27 1998-09-29 United Technologies Corporation Compact pressure balanced fulcrum-link nozzle
JP2003056403A (ja) * 2001-08-16 2003-02-26 Ishikawajima Harima Heavy Ind Co Ltd ジェットエンジン用排気ノズル
FR2857414B1 (fr) * 2003-07-08 2007-06-08 Snecma Moteurs Volet souple de tuyere a section variable de turbomachine
CA2547846A1 (fr) * 2003-12-01 2005-11-17 The University Of Mississippi Procede et dispositif de diminution du bruit de moteur
US7624567B2 (en) * 2005-09-20 2009-12-01 United Technologies Corporation Convergent divergent nozzle with interlocking divergent flaps
US8205454B2 (en) * 2007-02-06 2012-06-26 United Technologies Corporation Convergent divergent nozzle with edge cooled divergent seals
US7757477B2 (en) * 2007-02-20 2010-07-20 United Technologies Corporation Convergent divergent nozzle with slot cooled nozzle liner
US8572986B2 (en) * 2009-07-27 2013-11-05 United Technologies Corporation Retainer for suspended thermal protection elements in a gas turbine engine
US9810085B2 (en) 2011-08-22 2017-11-07 United Technologies Corporation Flap seal for gas turbine engine movable nozzle flap
US9163582B2 (en) * 2012-05-30 2015-10-20 United Technologies Corporation Convergent-divergent gas turbine nozzle comprising movable flaps having a variable thickness in a lateral direction
US9255548B2 (en) * 2012-09-11 2016-02-09 United Technologies Corporation Sliding U-joint hanger for gas turbine engine nozzle
WO2014185272A1 (fr) 2013-05-15 2014-11-20 株式会社Ihi Buse variable pour turbine à gaz d'avion

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1395800A (fr) * 1964-03-05 1965-04-16 Snecma Perfectionnements aux dispositifs d'attache du canal d'éjection des propulseurs à réaction ou autres canaux
US4176792A (en) * 1977-07-11 1979-12-04 General Electric Company Variable area exhaust nozzle
US5039014A (en) * 1989-04-11 1991-08-13 General Electric Company Axisymmetric vectoring exhaust nozzle seal
US4994660A (en) * 1989-04-11 1991-02-19 Hitachi, Ltd. Axisymmetric vectoring exhaust nozzle
US5076496A (en) * 1990-02-05 1991-12-31 General Electric Company Exhaust nozzle flap seal
US5082182A (en) * 1990-08-23 1992-01-21 United Technologies Corporation Thrust vectoring exhaust nozzle
EP0544764B1 (fr) * 1990-08-23 1995-11-08 United Technologies Corporation Tuyere axisymetrique avec anneau de commande synchronisee suspendu

Also Published As

Publication number Publication date
KR100263797B1 (ko) 2000-08-16
KR950702676A (ko) 1995-07-29
US5215256A (en) 1993-06-01
EP0674748A1 (fr) 1995-10-04
DE69313461T2 (de) 1998-03-19
JPH07509037A (ja) 1995-10-05
WO1994002731A1 (fr) 1994-02-03
DE69313461D1 (de) 1997-10-02
JP3200686B2 (ja) 2001-08-20
IL105263A (en) 1995-05-26

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